CN117703600A - Pintle type continuous rotation knocking space attitude control engine - Google Patents
Pintle type continuous rotation knocking space attitude control engine Download PDFInfo
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- CN117703600A CN117703600A CN202410179548.0A CN202410179548A CN117703600A CN 117703600 A CN117703600 A CN 117703600A CN 202410179548 A CN202410179548 A CN 202410179548A CN 117703600 A CN117703600 A CN 117703600A
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- fuel
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- sleeve
- cavity shell
- top cover
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- 239000000446 fuel Substances 0.000 claims abstract description 101
- 239000007800 oxidant agent Substances 0.000 claims abstract description 99
- 230000001590 oxidative effect Effects 0.000 claims abstract description 91
- 230000007246 mechanism Effects 0.000 claims abstract description 53
- 238000002485 combustion reaction Methods 0.000 claims abstract description 43
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 19
- 239000007921 spray Substances 0.000 claims abstract description 18
- 238000007789 sealing Methods 0.000 claims description 28
- 238000005474 detonation Methods 0.000 claims description 25
- 238000002347 injection Methods 0.000 abstract description 14
- 239000007924 injection Substances 0.000 abstract description 14
- 239000003380 propellant Substances 0.000 abstract description 12
- 230000008859 change Effects 0.000 abstract description 5
- 230000002035 prolonged effect Effects 0.000 abstract description 5
- 239000002699 waste material Substances 0.000 abstract description 4
- 238000003466 welding Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000004200 deflagration Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention belongs to the field of engines, in particular relates to a pintle type continuous rotation knocking space attitude control engine, and aims to solve the problems of extremely waste of propellant, low combustion efficiency and large combustion chamber quality in the prior art. The invention comprises the following steps: the servo mechanism is coaxially fixed with the top cover, the top cover is coaxially arranged with the oxidant cavity shell, and the oxidant cavity shell is coaxially arranged with the fuel cavity shell; the servo mechanism is respectively connected with the sleeve and the central rod in a driving way, and the sleeve is coaxially provided with an oxidant flow passage; a fuel agent flow passage is arranged between the outer surface of the sleeve and the end surface of the fuel agent cavity shell on one side far away from the top cover at intervals; the fuel agent cavity shell is coaxially arranged with the spray pipe. The invention can change the injection areas of the oxidant runner and the fuel runner simultaneously, and the oxidant runner and the fuel runner are decoupled, so that the thrust-changing requirement is realized, the structural quality of the whole engine is reduced, and the on-orbit working life of the spacecraft is prolonged.
Description
Technical Field
The invention belongs to the field of space propulsion, and particularly relates to a pintle type continuous rotation knocking space attitude control engine.
Background
The space attitude control engine is widely applied to spacecrafts such as satellites, spacecrafts, carrier rockets and the like, and is a main power device for spacecrafts such as orbit correction, speed adjustment, attitude control, intersection docking and the like. In order to realize accurate control of the spacecraft, the space attitude control engine is required to have the capability of changing thrust, and the magnitude of the thrust can be accurately controlled; in addition, the attitude control engine needs to be started and shut down for a plurality of times during the on-orbit period, and the stability and reliability of the combustion process of the attitude control engine need to be further improved; finally, in order to improve the on-orbit operation life of the spacecraft, the mass of the spacecraft, particularly the mass of an engine needs to be controlled to the greatest extent, so that the attitude control engine needs to be simple in structure, avoid structural redundancy and improve the working performance (combustion efficiency) in a reasonable mode in the design process.
The variable thrust of the engine is achieved by varying the injection area of the propellant, most typically a pintle injector. The pintle injector controls the movement of the center rod through the connecting mechanism to change the injection area, and heretofore, the engine adopting the pintle injector never has the combustion instability phenomenon, and has good reliability and stability. However, at present, the design of the pintle injector generally only changes the injection area of one propellant, and the injection area of the other propellant is kept unchanged, so that the propellant with unchanged injection area is extremely wasted in the thrust-changing process, the combustion is unfavorable and efficient, and the service life of the spacecraft is prolonged; furthermore, even though some designs may change the injection area of two propellants simultaneously, there is still a certain correlation between the injection areas of the two, which easily results in that the propellants can only be mixed in certain fixed proportions, the variable thrust of which is limited to a fixed value.
The traditional combustion and heat release process of the propellant in the space attitude control engine is a deflagration combustion process, and the combustion efficiency of the combustion mode is quite limited at present. The thermodynamic cycle efficiency of the continuous rotary detonation engine adopting the detonation combustion mode is higher than that of the continuous rotary detonation engine adopting the detonation combustion mode, and the heat release rate is higher, so that the combustion efficiency is improved obviously; furthermore, classical continuous rotary detonation engines employ annular barrel combustors to limit the spatial location of combustion heat release, thereby producing self-sustaining continuous rotary detonation waves. The length of the combustion chamber is longer, so that the length of the combustion chamber is expected to be further shortened, and the overall structural quality is reduced.
Based on the above, the invention provides a pintle type continuous rotation knocking space attitude control engine.
Disclosure of Invention
In order to solve the problems in the prior art, namely the problems of extremely waste of propellant, low combustion efficiency and large combustion chamber mass in the prior art, the invention provides a pintle type continuous rotary detonation space attitude control engine, which comprises a servo mechanism, a top cover, an oxidant cavity shell, a fuel cavity shell, a sleeve, a center rod and a spray pipe;
the servo mechanism is coaxially fixed with the top cover, the top cover is coaxially arranged with the oxidant cavity shell and is detachably and fixedly connected with the oxidant cavity shell, and the oxidant cavity shell is coaxially arranged with the fuel cavity shell and is detachably and fixedly connected with the fuel cavity shell;
the servo mechanism is respectively connected with the sleeve and the central rod in a driving way, and the central rod can move along the sleeve; the sleeve can move along the fuel agent cavity shell, an oxidant flow passage is coaxially formed in the sleeve, the oxidant flow passage is communicated with the oxidant cavity, the oxidant cavity is coaxially formed in the oxidant cavity shell, and the oxidant cavity is used for adding an oxidant;
a fuel flow passage is arranged between the outer surface of the sleeve and the end surface of the fuel cavity shell, which is far away from the top cover, at intervals, the fuel flow passage is communicated with the fuel cavity, the fuel cavity is coaxially arranged in the fuel cavity shell, and the fuel cavity is used for adding a fuel;
the fuel agent cavity shell is coaxially arranged with the spray pipe and is detachably and fixedly connected with the spray pipe, and the spray pipe is used for realizing combustion of the oxidant and the fuel agent.
In some preferred embodiments, the servomechanism is drivingly connected to the sleeve and the central rod, respectively, in such a way that:
the servo mechanism is respectively in driving connection with one end of the sleeve moving mechanism and one end of the center rod moving mechanism, the other end of the sleeve moving mechanism penetrates through the top cover to be fixed with the sleeve connecting mechanism, and the sleeve connecting mechanism penetrates through the oxidant cavity shell to be fixed with the sleeve;
the other end of the center rod moving mechanism penetrates through the sleeve connecting mechanism to be fixed with the center rod.
In some preferred embodiments, the sleeve connection mechanism is secured to the sleeve through the oxidant chamber housing in the following manner:
the end face, close to one side of the top cover, of the oxidant cavity shell is provided with a through hole, the inner surface of the through hole is fixed with the outer surface of the first joint, and the inner surface of the first joint is in sliding sealing connection with the sleeve connecting mechanism through a first sliding sealing device.
In some preferred embodiments, a first radial seal groove is formed in an end face of the top cover, which is attached to the oxidant chamber housing, and is used for realizing sealing connection between the top cover and the oxidant chamber housing.
In some preferred embodiments, a second radial seal groove is formed on the end face of the oxidant chamber housing, which is attached to the fuel chamber housing, and is used for realizing the sealing connection between the oxidant chamber housing and the fuel chamber housing.
In some preferred embodiments, a third radial sealing groove is formed in the end face, attached to the nozzle, of the fuel agent chamber housing, and is used for achieving sealing connection between the fuel agent chamber housing and the nozzle.
In some preferred embodiments, a second sliding seal is provided between the outer surface of the sleeve and the end face of the fuel chamber housing on the side close to the top cover, said second sliding seal being used to achieve a sliding seal between the sleeve and the fuel chamber housing.
In some preferred embodiments, the oxidant chamber housing and the fuel chamber housing are provided with an oxidant inlet fitting and a fuel inlet fitting, respectively;
the oxidant inlet connector is in sealing connection and fixed with the oxidant inlet, and the oxidant inlet is formed in the outer circumferential surface of the oxidant cavity shell;
the fuel inlet connector is connected with and fixed to the fuel inlet in a sealing mode, and the fuel inlet is formed in the outer circumferential surface of the fuel cavity shell.
In some preferred embodiments, a conical head is fixed to the end of the central rod disposed within the nozzle, by means of which conical head a conical combustion chamber is formed within the nozzle for achieving continuous rotary detonation combustion.
In some preferred embodiments, the oxidant inlet connector, the oxidant inlet, the fuel inlet connector and the fuel inlet are symmetrically disposed in two groups along the axis of the central rod.
The invention has the beneficial effects that:
1. with a pintle injector, the servo mechanism may simultaneously control the precession of the sleeve and the central rod in the axial direction. When the sleeve is not moved, the central rod moves up and down, so that the injection area of the oxidant flow channel can be changed, and the thrust is changed; when the sleeve moves up and down and the central rod is not moved, the injection areas of the oxidant runner and the fuel runner can be changed at the same time, so that the variable thrust combustion is realized. These two cases are functions that can be realized by a general pintle injector, and the defects in these cases have been pointed out above, and the pintle injector of the present patent can also perform a third case, that is, control the upward and downward movements of the sleeve and the center rod simultaneously, that is, can change the injection areas of the oxidant runner and the fuel runner simultaneously, and the two are decoupled, thereby realizing the requirement of changing the thrust. In addition, by adopting the mode, the injector can be adjusted to the optimal design working condition, so that the requirement of accurate thrust can be realized, the waste of the propellant can be avoided, and the on-orbit working life of the spacecraft can be prolonged;
2. the pintle type injector is adopted, and the problem of unstable combustion of an engine adopting the injector does not exist at present, so that the combustion stability and reliability of the injector are enhanced, and the requirements of repeated shutdown and starting of the engine can be met;
3. the spray pipe is designed into a conical spray pipe, the head part of the central rod is also a conical head part, so that the mixing process between propellants can be enhanced, the combustion area is limited, and the result of hot test shows that continuous rotary detonation combustion can occur;
4. compared with the traditional deflagration combustion organization mode, the detonation combustion organization mode has the advantages of high thermodynamic cycle efficiency, high heat flux density and high heat release efficiency, is beneficial to improving the combustion efficiency and prolonging the on-orbit working life of the spacecraft;
5. by adopting a rotary knocking mode, the combustion of fuel and oxidant occurs at the head of the combustion chamber, so that the length of straight sections such as the combustion chamber can be reduced, the structural quality of the whole engine is lightened, and the on-orbit service life of the spacecraft is prolonged;
6. the invention has high modularization degree, simple and compact structure, good stability and important economic and engineering application values.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, made with reference to the following drawings, in which:
FIG. 1 is an isometric view of a pintle type continuous rotation detonation space attitude control engine of the present invention;
FIG. 2 is a schematic diagram of the internal structure of a pintle type continuous rotation detonation space attitude control engine of the present invention;
FIG. 3 is a schematic illustration of a sleeve connection mechanism for a pintle type continuous rotation detonation space attitude control engine of the present invention.
Detailed Description
The present application is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to fig. 1-3, referring to fig. 1, the invention provides a pintle type continuous rotary detonation space attitude control engine, which comprises a servo mechanism 1, a top cover 3, an oxidant cavity shell 6, a fuel cavity shell 7, a sleeve 8, a central rod 10 and a spray pipe 13;
the servo mechanism 1 is coaxially fixed with the top cover 3, the top cover 3 is coaxially arranged with the oxidant cavity shell 6 and is detachably and fixedly connected with the oxidant cavity shell 6, and the oxidant cavity shell 6 is coaxially arranged with the fuel cavity shell 7 and is detachably and fixedly connected with the fuel cavity shell 7;
the servo mechanism 1 is respectively connected with the sleeve 8 and the central rod 10 in a driving way, and the central rod 10 can move along the sleeve 8; the sleeve 8 can move along the fuel agent cavity shell 7, an oxidant flow passage 51 is coaxially arranged on the sleeve 8, the oxidant flow passage 51 is communicated with the oxidant cavity 5, the oxidant cavity 5 is coaxially arranged in the oxidant cavity shell 6, and the oxidant cavity 5 is used for adding an oxidant;
a fuel flow passage 91 is arranged between the outer surface of the sleeve 8 and the end surface of the fuel cavity shell 7, which is far away from the top cover 3, the fuel flow passage 91 is communicated with the fuel cavity 9, the fuel cavity 9 is coaxially arranged in the fuel cavity shell 7, and the fuel cavity 9 is used for adding fuel;
the fuel agent cavity shell 7 is coaxially arranged with the spray pipe 13 and is detachably and fixedly connected, and the spray pipe 13 is used for realizing the combustion of the oxidant and the fuel agent.
Wherein the servo 1 can simultaneously control the precession of the sleeve 8 and the central rod 10 in the axial direction. When the sleeve 8 is not moving, the central rod 10 moves up and down, so that the injection area of the oxidant flow channel 51 can be changed, and the thrust is changed; when the sleeve 8 moves up and down the center rod 10, the injection areas of the oxidant flow passage 51 and the fuel flow passage 91 can be changed simultaneously, thereby realizing variable thrust combustion. These two cases are functions that can be achieved by a general pintle injector, and the disadvantages of these cases have been pointed out above, and the pintle injector of the present patent can also perform the third case, that is, control the upward and downward movements of the sleeve 8 and the center rod 10 simultaneously, that is, can change the injection areas of the oxidant flow channel 51 and the fuel flow channel 91 simultaneously, and decouple the two, so as to achieve the requirement of changing the thrust. In addition, by adopting the mode, the injector can be adjusted to the optimal design working condition, so that the requirement of accurate thrust can be realized, the waste of the propellant can be avoided, and the on-orbit working life of the spacecraft can be prolonged.
Wherein, sleeve 8 can follow fuel agent chamber casing 7 removes, and its specific structure is:
the surface of the fuel chamber housing 7 near the oxidant chamber housing 6 is provided with a guide hole matching with the shape of the outer surface of the sleeve 8, and the sleeve 8 moves along the guide hole.
As a further explanation of the invention, see fig. 1, 2 and 3, the servomechanism 1 is in driving connection with the sleeve 8 and the central rod 10, respectively, in such a way that:
the servo mechanism 1 is respectively in driving connection with one end of the sleeve moving mechanism 11 and one end of the center rod moving mechanism 12, the other end of the sleeve moving mechanism 11 penetrates through the top cover 3 to be fixed with the sleeve connecting mechanism 2, and the sleeve connecting mechanism 2 penetrates through the oxidant cavity shell 6 to be fixed with the sleeve 8;
the other end of the center rod moving mechanism 12 is fixed to the center rod 10 through the socket joint mechanism 2.
In this embodiment, referring to fig. 2 and 3, the other end of the sleeve moving mechanism 11 passes through the top cover 3 and is fixed to the sleeve connecting mechanism 2, and the specific structure thereof is as follows:
the sleeve connecting mechanism 2 comprises a first disc 22 and a support 23 fixed with the first disc 22;
at least 4 groups are uniformly arranged at one end of the support column 23 along the circumferential surface of the first disc 22, the other end of the sleeve moving mechanism 11 is welded and fixed with the upper end welding port 21, the upper end welding port 21 is arranged on the first disc 22, and at least 4 groups are uniformly arranged at the upper end welding port 21 and the sleeve moving mechanism 11 along the circumferential direction of the center of the first disc 22.
In this embodiment, the sleeve connection mechanism 2 is fixed to the sleeve 8 through the oxidant chamber housing 6, and has a specific structure as follows:
the other end of the support 23 is welded and fixed with a sleeve welding hole 81, the sleeve welding hole 81 is formed in the upper end face of the sleeve 8, and at least 4 groups of sleeve welding holes 81 are uniformly formed along the central circumference of the first disc 22.
In this embodiment, the other end of the center rod moving mechanism 12 passes through the sleeve connecting mechanism 2 to be fixed with the center rod 10, and the specific structure thereof is as follows:
the center rod moving mechanism 12 is welded and fixed with the center rod welding port 102, and the center rod welding port 102 is opened at one end of the center rod 10.
In this embodiment, the top cover 3 and the oxidant chamber housing 6 are provided with a first threaded hole 32, and the detachable fixation of the top cover 3 and the oxidant chamber housing 6 is achieved through the first threaded hole 32, and the first threaded holes 32 are uniformly provided with multiple groups along the circumferential direction of the top cover 3.
In this embodiment, the oxidant chamber housing 6 and the fuel chamber housing 7 are provided with second threaded holes 71, and the oxidant chamber housing 6 and the fuel chamber housing 7 are detachably fixed by the second threaded holes 71, and the second threaded holes 71 are uniformly provided with multiple groups along the circumferential direction of the oxidant chamber housing 6.
In this embodiment, the fuel chamber housing 7 and the nozzle 13 are provided with a third threaded hole 111, and the fuel chamber housing 7 and the nozzle 13 are detachably fixed by the third threaded hole 111, and multiple groups of third threaded holes 111 are uniformly arranged along the circumferential direction of the fuel chamber housing 7.
As a further explanation of the invention, referring to fig. 2, the sleeve connection mechanism 2 is fixed to the sleeve 8 through the oxidizer chamber housing 6 in such a manner that:
the end face of the oxidant cavity shell 6, which is close to one side of the top cover 3, is provided with a through hole, the inner surface of the through hole is fixed with the outer surface of the first joint 4, and the inner surface of the first joint 4 is in sliding sealing connection with the sleeve connecting mechanism 2 through a first sliding sealing device 41.
Wherein, in the present embodiment, the inner surface of the first joint 4 is in sliding sealing connection with the supporting column 23 through a first sliding sealing device 41, and the first joint 4 and the first sliding sealing device 41 are uniformly provided with at least 4 groups along the central circumference of the first disc 22;
the first sliding seal device 41 is a seal groove formed on the inner surface of the first joint 4.
As a further explanation of the present invention, referring to fig. 2, a first radial seal groove 31 is formed on an end surface of the top cover 3, which is attached to the oxidizer chamber housing 6, and the first radial seal groove 31 is used to realize a sealing connection between the top cover 3 and the oxidizer chamber housing 6.
As a further explanation of the present invention, referring to fig. 2, a second radial seal groove 64 is provided on the end face of the oxidizer chamber housing 6 that is in contact with the fuel chamber housing 7, and the second radial seal groove 64 is used to realize a sealing connection between the oxidizer chamber housing 6 and the fuel chamber housing 7.
As a further explanation of the present invention, referring to fig. 2, a third radial seal groove 75 is formed on the end surface of the fuel chamber housing 7 that is attached to the nozzle 13, and the third radial seal groove 75 is used to realize a sealing connection between the fuel chamber housing 7 and the nozzle 13.
As a further explanation of the invention, referring to fig. 2, a second sliding seal 72 is provided between the outer surface of the sleeve 8 and the end surface of the fuel chamber housing 7 on the side close to the top cover 3, the second sliding seal 72 being used to achieve a sliding seal between the sleeve 8 and the fuel chamber housing 7.
Wherein the second sliding seal device 72 is a seal groove formed on the surface of the guide hole.
As a further explanation of the present invention, referring to fig. 2, the oxidizer chamber housing 6 and the fuel chamber housing 7 are provided with oxidizer inlet joint 63 and fuel inlet joint 73, respectively;
the oxidant inlet connector 63 is in sealing connection and fixed with the oxidant inlet 62, and the oxidant inlet 62 is formed on the outer circumferential surface of the oxidant cavity shell 6;
the fuel inlet joint 73 is connected and fixed with a fuel inlet 74 in a sealing manner, and the fuel inlet 74 is formed on the outer circumferential surface of the fuel chamber housing 7.
As a further explanation of the present invention, referring to fig. 2, a conical head 101 is fixed to one end of the central rod 10 disposed in the nozzle 13, and a conical combustion chamber 112 is formed in the nozzle 13 by the conical head 101, and the conical combustion chamber 112 is used to realize continuous rotary detonation combustion.
Wherein, the conical combustion chamber 112 is communicated with a throat 113, the throat 113 is coaxially arranged on the spray pipe 13, and the throat 113 is used for converting the internal energy generated by the conical combustion chamber 112 into kinetic energy.
As a further explanation of the present invention, referring to fig. 2, the oxidant inlet connection 63, the oxidant inlet 62, the fuel inlet connection 73 and the fuel inlet 74 are symmetrically arranged in two groups along the axis of the central rod 10.
The terms "first," "second," and the like, are used for distinguishing between similar objects and not for describing a particular sequential or chronological order.
The terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus/apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus/apparatus.
Thus far, the technical solution of the present invention has been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of protection of the present invention is not limited to these specific embodiments. Equivalent modifications and substitutions for related technical features may be made by those skilled in the art without departing from the principles of the present invention, and such modifications and substitutions will be within the scope of the present invention.
Claims (10)
1. The pintle type continuous rotation knocking space attitude control engine is characterized by comprising a servo mechanism (1), a top cover (3), an oxidant cavity shell (6), a fuel cavity shell (7), a sleeve (8), a center rod (10) and a spray pipe (13);
the servo mechanism (1) is coaxially fixed with the top cover (3), the top cover (3) is coaxially arranged with the oxidant cavity shell (6) and is detachably and fixedly connected, and the oxidant cavity shell (6) is coaxially arranged with the fuel cavity shell (7) and is detachably and fixedly connected;
the servo mechanism (1) is respectively connected with the sleeve (8) and the central rod (10) in a driving way, and the central rod (10) can move along the sleeve (8); the sleeve (8) can move along the fuel agent cavity shell (7), an oxidant flow passage (51) is coaxially formed in the sleeve (8), the oxidant flow passage (51) is communicated with the oxidant cavity (5), the oxidant cavity (5) is coaxially formed in the oxidant cavity shell (6), and the oxidant cavity (5) is used for adding an oxidant;
a fuel flow passage (91) is arranged between the outer surface of the sleeve (8) and the end surface of the fuel cavity shell (7) at one side far away from the top cover (3), the fuel flow passage (91) is communicated with a fuel cavity (9), the fuel cavity (9) is coaxially arranged in the fuel cavity shell (7), and the fuel cavity (9) is used for adding a fuel;
the fuel agent cavity shell (7) is coaxially arranged with the spray pipe (13) and is detachably and fixedly connected, and the spray pipe (13) is used for realizing the combustion of the oxidant and the fuel agent.
2. A pintle type continuous rotation detonation space attitude control engine according to claim 1, characterized in that said servomechanism (1) is in driving connection with said sleeve (8) and said central rod (10), respectively, in such a way that:
the servo mechanism (1) is respectively connected with one end of the sleeve moving mechanism (11) and one end of the center rod moving mechanism (12) in a driving way, the other end of the sleeve moving mechanism (11) penetrates through the top cover (3) to be fixed with the sleeve connecting mechanism (2), and the sleeve connecting mechanism (2) penetrates through the oxidant cavity shell (6) to be fixed with the sleeve (8);
the other end of the center rod moving mechanism (12) passes through the sleeve connecting mechanism (2) to be fixed with the center rod (10).
3. A pintle type continuous rotation detonation space attitude control engine according to claim 2, characterized in that said sleeve connection mechanism (2) is fixed with said sleeve (8) through said oxidizer chamber housing (6) in such a way that:
the end face, close to one side of the top cover (3), of the oxidant cavity shell (6) is provided with a through hole, the inner surface of the through hole is fixed with the outer surface of the first joint (4), and the inner surface of the first joint (4) is in sliding sealing connection with the sleeve connecting mechanism (2) through a first sliding sealing device (41).
4. A pintle type continuous rotation detonation space attitude control engine according to claim 3, characterized in that a first radial seal groove (31) is formed on the end face of the top cover (3) attached to the oxidant cavity shell (6), and the first radial seal groove (31) is used for realizing sealing connection between the top cover (3) and the oxidant cavity shell (6).
5. The pintle type continuous rotation detonation space attitude control engine according to claim 4, wherein a second radial seal groove (64) is formed on the end face of the oxidant cavity shell (6) attached to the fuel cavity shell (7), and the second radial seal groove (64) is used for realizing sealing connection between the oxidant cavity shell (6) and the fuel cavity shell (7).
6. The pintle type continuous rotation detonation space attitude control engine according to claim 5 is characterized in that a third radial seal groove (75) is formed in the end face, attached to the spray pipe (13), of the fuel agent cavity shell (7), and the third radial seal groove (75) is used for realizing sealing connection between the fuel agent cavity shell (7) and the spray pipe (13).
7. The pintle type continuous rotation detonation space attitude control engine according to claim 6, wherein a second sliding sealing device (72) is arranged between the outer surface of the sleeve (8) and the end face of the fuel agent cavity shell (7) close to the top cover (3), and the second sliding sealing device (72) is used for realizing sliding sealing between the sleeve (8) and the fuel agent cavity shell (7).
8. The pintle type continuous rotation detonation space attitude control engine according to claim 7, wherein an oxidant inlet joint (63) and a fuel inlet joint (73) are respectively arranged on the oxidant cavity housing (6) and the fuel cavity housing (7);
the oxidant inlet connector (63) is connected with the oxidant inlet (62) in a sealing way and is fixed, and the oxidant inlet (62) is formed in the outer circumferential surface of the oxidant cavity shell (6);
the fuel inlet connector (73) is connected with and fixed to the fuel inlet (74) in a sealing mode, and the fuel inlet (74) is formed in the outer circumferential surface of the fuel cavity shell (7).
9. The pintle type continuous rotation detonation space attitude control engine according to claim 8, wherein one end of the center rod (10) arranged in the spray pipe (13) is fixed with a conical head (101), a conical combustion chamber (112) is formed in the spray pipe (13) through the conical head (101), and the conical combustion chamber (112) is used for realizing continuous rotation detonation combustion.
10. The pintle type continuous rotation detonation space gesture control engine of claim 9 wherein the oxidant inlet joint (63), the oxidant inlet (62), the fuel inlet joint (73) and the fuel inlet (74) are symmetrically arranged in two groups along the axis of the central rod (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410179548.0A CN117703600B (en) | 2024-02-18 | 2024-02-18 | Pintle type continuous rotation knocking space attitude control engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410179548.0A CN117703600B (en) | 2024-02-18 | 2024-02-18 | Pintle type continuous rotation knocking space attitude control engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117703600A true CN117703600A (en) | 2024-03-15 |
| CN117703600B CN117703600B (en) | 2024-04-30 |
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|---|---|---|---|
| CN202410179548.0A Active CN117703600B (en) | 2024-02-18 | 2024-02-18 | Pintle type continuous rotation knocking space attitude control engine |
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